The Boeing Company

Paul R Smith

Patrick M Fahey

Gen Matsui

Patrick Joseph McCormick

Mark William Lesyna

Tristan E Lee

Jerry Edward Farstad

Matthew D Uhlman

Ernest H Kanning

Barry D Hance

Christopher P Beamis

Victoria L Garcia

Michel G Malett

Adam C Steele

Ryan W Hoffman

Ali Abdelmagid

Kyle M Fanelli

Drew M Thompson

Herbert Guttler

John D Farmer

Frank L Wichman

Robert J Hawk

Kenneth B Dunkelberg

Kyle A Peterson

Ellen A Pifer

Joel R Will

A hydraulic system for a vehicle includes a hydraulic monitoring control unit configured to receive an operational signal from a sub-system of the vehicle and control flow of hydraulic fluid to actuators of components based on the operational signal. The hydraulic monitoring control unit is configured to bypass the flow of the hydraulic fluid in relation to a subset of the actuators in response to the operational signal indicating an altered operational state of the sub-system.

Hydraulic control systems and methods for components of an aircraft

A hydraulic system (e.g., of an aircraft or other vehicle) includes a pump, a pressure line coupled to the pump and configured to distribute pressurized hydraulic fluid, and a return line configured to return hydraulic fluid to a reservoir. The hydraulic system also includes an auxiliary leakage valve coupled to the pressure line, to the return line, and to an actuator. The auxiliary leakage valve is configured to receive a control signal and, based on the control signal, selectively open a restricted fluid path. The restricted fluid path couples the pressure line to the return line to allow a restricted amount of the hydraulic fluid to flow from the pressure line to the return line.

Hydraulic fluid warming system and method

An example system for disconnecting a driven member from a driving member is described. The system includes a vibration detection device configured to output vibration signals indicative of vibration levels of the driven member. The system also includes a controller including at least one processor. The controller is arranged to (i) determine that a vibration signal output by the vibration detection device satisfies a threshold condition and (ii) based at least on the determination that the vibration signal satisfies the threshold condition, trigger a mechanical disconnection of the driven member from the driving member by a mechanical disconnect device.

Engine accessory disconnect system

A method includes receiving characteristic information from a sensor. The characteristic information may be representative of a characteristic of a weight bearing structure of an aircraft when a force is applied to the weight bearing structure. The method includes determining a weight of the aircraft based on the characteristic information. The method includes receiving attitude information from an attitude sensor. The attitude information indicates whether the aircraft is situated on a level surface. The method includes determining a balance condition based on the attitude information and the weight of the aircraft. The balance condition indicates whether the weight of the aircraft is distributed evenly. The method includes generating an alert when the balance condition indicates that the weight of the aircraft is not distributed evenly.

Modal acoustic aircraft weight system

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Everett, WA, United States of America

Paul R Smith